کد مقاله | کد نشریه | سال انتشار | مقاله انگلیسی | نسخه تمام متن |
---|---|---|---|---|
7706614 | 1497310 | 2018 | 10 صفحه PDF | دانلود رایگان |
عنوان انگلیسی مقاله ISI
Hydrogen-fueled detonation ramjet model: Wind tunnel tests at approach air stream Mach number 5.7 and stagnation temperature 1500Â K
دانلود مقاله + سفارش ترجمه
دانلود مقاله ISI انگلیسی
رایگان برای ایرانیان
کلمات کلیدی
موضوعات مرتبط
مهندسی و علوم پایه
شیمی
الکتروشیمی
پیش نمایش صفحه اول مقاله
![عکس صفحه اول مقاله: Hydrogen-fueled detonation ramjet model: Wind tunnel tests at approach air stream Mach number 5.7 and stagnation temperature 1500Â K Hydrogen-fueled detonation ramjet model: Wind tunnel tests at approach air stream Mach number 5.7 and stagnation temperature 1500Â K](/preview/png/7706614.png)
چکیده انگلیسی
The mode of continuous spinning detonation (CSD) combustion of hydrogen in the annular combustor of a model of a hydrogen-fueled detonation ramjet under conditions of approach air stream Mach number 5.7 and stagnation temperature 1500Â K is registered experimentally in a short-duration (pulsed) wind tunnel at the overall air-to-hydrogen equivalence ratio (ER) ranging from 0.7 to 1.4. The maximum values of thrust and specific impulse of the ramjet model are attained at ERÂ =Â 1.25 and are estimated as 1550Â N and 3300Â s, respectively. At 1.4Â <Â ERÂ <Â 1.6, the mode of longitudinally pulsating detonation (LPD) combustion is registered with somewhat lower values of thrust and specific impulse.
ناشر
Database: Elsevier - ScienceDirect (ساینس دایرکت)
Journal: International Journal of Hydrogen Energy - Volume 43, Issue 15, 12 April 2018, Pages 7515-7524
Journal: International Journal of Hydrogen Energy - Volume 43, Issue 15, 12 April 2018, Pages 7515-7524
نویسندگان
S.M. Frolov, V.I. Zvegintsev, V.S. Ivanov, V.S. Aksenov, I.O. Shamshin, D.A. Vnuchkov, D.G. Nalivaichenko, A.A. Berlin, V.M. Fomin, A.N. Shiplyuk, N.N. Yakovlev,